Aeroplane.



J. B. GROSS.

AEROPLANE.

APPUCATION FILED Nov. 30, 1914.

Patented Jan. 4, 1916 6 SHEETS-SHEU I.

A TTORNE w WITNESSES J. B. GRGSS.

AEROPLANE.

APPLICATION FILED NOV. 30. 19-14.

Patented Jan. 4; 1916.

6 SHEET HEETZ.

' WITNESSES A TTOH/VEYS .zww

J. B. GROSS.

AEROPLANE.

APPLICATION FILED NOV. 30, 1914.

1,167,293. v Tatnted Jan. 4, 1916.

6 SHEETSSHEET 3.

' ATTOR EYS I WI T/VESSES J. B. enoss.

' AEROPLANE. APPLICATION FILED NOV. 30. 1914.

Patented Jan. 4, 1916.

.6 SHEETS-SHEET 4.

i INVENTOR J. B. GROtSb.

AERUPLANE,

APPLICATION FI ED NOV. 30. I914 Z141 Wit-23%, Patented. Jan. 4, 1916.

e SHEETS-SHEET s.

WITNESSES A TTORNEYS V Z Z223 BY 7 J; B GROSS. AE ROPLANE. APPLICATIONFILED NOV, 30, -19 14.

Patented Jan. 4, 1916. 6 ShEETS-SHEET I @Qrw W HQ A NOR/VH8 JOHN B.GROSS, OF NEW YGRK,

N. Y., .ASSIGNOR 'ro JOSEPH w. CONNELLY, or J RSEY CITY, NEW JERSEY.

- AEROPLANE.

A further object is to provide means for warping thecnds of thesustaining planes in the proper directions and degrees simultaneously.

A further' object is to provide ailerons which are movable into and outof horizonan" planes both longitudinally and laterally of the aeroplane.

A. further object is to provide new and improved means for taking theimpact of landing; and other objects 'are to provide such devices whichare simple in construction and operation, under ositive control to meetall atmospheric conditions, and com; .paratively inexpensive.

My invention is, fully described in the following specification, ofwhich the accompanying drawings form a part, in which the separate partsare designated by the same reference characters in each of the views,and in which Figure 1 is a side elevation of an aeroplane constructed inaccordance with my present invention; Fig. 2 is a fragmentary plan viewthereof; Fi 3 is an enlarged side elevation of the orward aeroplane;Fig. 4- is an enlarge perspective, 'VIGW of a detai detached, of the'con- 'struction; F1 5 is a section taken on the line 5-5 of ig. 1; Fig.6 is an enlarged section taken on the line 6-6 of Fig. '3; Fig. 7 is asimilar view taken on the line 7 7 of Fig. 5; Fig. 8 is a section takenon the line 8-8 of F 1g. 1; Fi 9 is a section taken on the line 9-9 ofig. 1; Fig. 10 is a diagrammatic view of one control; Fig. 11 isadiagrammatic view of another control; Fig; 12 is a. fragmentary,sectional,

view of a detail; and Fig. 13 is an enlarged section taken on the line13-13 of Fig. 12.

In the drawings forming a part-of this Specification of Letters Patent.

art of the -vating planes 29 carried b Patented Jan. 4,1916.

Application filed November 30, 1914. Serial No. 874,699.

application I have. shown a present preferred form of embodiment ofmyinvention, comprising a suitable frame 14 havin vertically movablelanding wheels 15 shdable in guiding supports 16 and normally maintainedat their l west points by springs 17, n order that a landing may betaken without ars, and I also provide landing shoes or runners 18adapted to limit tiw {five to the wheels 15; at the rear (,i the frame14 is a fixed wheel 19 and resilient runners 20 operating in conjunctiontherewith, and it will thus be seen that the impact of landing is takenresiliently both in the forward part and rear part of the aeroplane.

The frame is ailVlded with oppositely and transversely. directed arms 21and 22 which rigidly support the main sustaining planes 23 along theaxial line thereof, but

without interference with the movement of the ends of'said planes in arotary direction with respect to said axis, orsaid arms, said planes 23being mounted approximately midway of the forward and rear ends of theaeroplane.

Similarly carried by the frame 14, directly tothe rear of the mainplanes 23 are sim1- lar but shorter auxiliary planes 24, the formerbeing preferably on a slightly higher level than the latter, as shown inFig. 1, and the propellers 25 are arranged between said main andauxiliary planes,-one on each side of the central plane of theaeroplane,on shafts 26 actuated by belts 27 in operative connection witha motor 28 in any desired manner, this propeller arrangement, as alsothat of the motor, and the types thereof,

being entirely optional with me, as;I claim no novelty therein.

Rear-ward of the planes 24' are rear elea shaft 30 rotatab n saidframe-14, Figs. 2 and 9, and to the rear thereof is the rudder 31carried by a vertical shaft '32 and the o crating means of which will belater descri ed.

Pivotally mounted in 'a fixed, vertical, portion 33 of the frame 14,forwardly of the main planes 23', is a forwardly directed lever 34.-which has a. journal 35 turned thereon for a frame 36 the arms of whichare outwardly and transversely directed and carry, each, an aileron 37,'and it will be seen that the frame 36 may be revolved through adesired are of a circle on its journahIthus moving one aileron 37upwardly and; the

segment gear, 51

. horizonta able guide staples orapu eys,

other downwardly of the horizontal, lateral,

plane of the aeroplane, and it will also be seen -that,. 'if the-lever3-1 be raised or lowered, in a manner to be described, the aileandaap'ted to be moved. into and out of a horizontal, longitudinahplane ofthe, aeroplane aslater set forth, and I prefer to shape the elevatingplane 38 as illustrated in Fig. 2.

The frame} 1 1 carries three vertical supports -10, 41, and 42, suitablybraced, and to the first of'which is pivoted, at 43, a normallyhorizontal lever 44 carrying a vertical arm 45 and likewise pivoted tothe frame 39 of the plane 38, thus insuring the actuation of said lane38 in the movement of said lever; this ever.

is provided with a short. length of cable 47 passed taut around a pulleyl8 revoluble on the su port 40, Figs; 1, 3, 5 and 6, and adapted to e.so revolvedby means of a lever i9 provided .with a pawl whereby thelever 49 and connected parts may be locked in any de sired position. H

The forward end of the lever has a link ,52 in pivotal connectiontherewith in turnpivotedto the lever 34, and it will be seen that,when-this elevating plane is actuated on its pivot, theailerons. 37 aremoved accordingly into or out of the longitudinal,

l, plane of the aeroplane. The verticalsnpportntl also carries a pulley.53 adapted to be actuated by means of a lever 54 provided with a pawl 55in operation with a segment gear 56, a cable 57 being passed around.thispulle and, through .suitto a pulley 58 on a shaft 59 carrying an arm60 in pivotal connection at its end with a link 61 likewise pivoted tothe rear elevating planes 29 whereby they may be moved into or out ofthe horizontal, longitudinal, lane of the aeroplane at will, and it.williie noted that these control levers are to a drivers or pilots seat62.Also'located conveniently thereto; and carried on the vertical support40, are two pulleys 63 and '64, Figs. 5 and 7, the former of whichisadapted. to be revolved by .means of a double winged lever 65 having athereto at each links being in-pivotal connection with vertical rods'67inturn pivoted to corresponding arms of the aileron frame-36, Fig. 5,said lever fic having pawlsithereoa operating in ock conjunction with asegment gear-68 to plane of the aeroplane,

intoor out Ofthe lateraI horizontal, plane re-' to which is pivoted alink 46 50 operating over located conveniently linkGS pivoted side ofits fulcrum, saidsaid aileron frame 36 in any desired position, in orout of the lateral, horizontal, without interference with the rotarymovement of said frame 36 in its pivotal connection, through the lever34. with the frame portion The pulley ()3 has a cable (59 passedthereover and extended downwardly on either sidctherecf to correspondingarms 70 secured to a longitudinally arranged shaft 71, Figs. 1, 5,'andl1, and the rear end of which carries two .pulleys 72 and 73, a cable 74being passeclaround the former and upwardly through guides carried bythe vertical support ll and downwardly into connection with theforward-corners of the ends of the main planes '23 in such manner that,

when the shaft is rotated to revolve the pulguides in the verticalsupport 42- and thence.

downwardly for connection with the forward corners of the ends of theauxiliary 2 planes 24, and it will be seen that these planes aredistorted with the main planes, and with the tilting laterally of theforwardly aileron frame 36. The pulley 73 has a cable 76 connectedtherewith and which is passed, in the manner of the cable 74, to therear corners of the ends of the main planes, and branch cablesTT securedthereto pass to the auxiliary planes, at the rear corners of the endsthereof, pulleys T2 and 73 being so arranged as to exert strains onopposite ends of the main and auxiliary planes, in the rotation of theshaft 71 in either direction, whereby one corner of each end of eachplane is raised, and the other corner lowered, and the forward aileronsare correspondingly ailected.

The pulley G4, on the support 40, Figs. 1, 2, 7 andlO, has a cable 78connected there: with-and passed rearwardly to and around a pulley 79onthe shaft rudder shaft 32, and it-will be thus seen that the rudder 31may be swung in the desired relationship with the aeroplane. It willalso be seen that, from the pilots seat, the forward elevating plane maybe moved'in desired direction and degree, the ailerons beingcorrespondingly and simultaneously actuated in a rotary manner withrespect to the transverse axis thereof; the movement of the forward Iaileron frame synchronizes with the distortion of the ends of the mainand auxiliary sustaining planes; and the rear elevating planes 29 may beindependently aetuated in desired manner and degree, and absolutecontrolresults, as also positive'stability, but under the control of thepi-lot.:

Because of the relatively great area of the sustaining planes,myaeroplane will support verygreat loads, and it is very simple saidcables of the Cit that I do not limit myself thereto, but may.

make changes thereover, within the scope of the following claims,without departing from the spirit of my invention, or sacrificing itsadvantages. 7

Having fully described my invention, what I claim as new, and desire tosecure by Letters Patent, is

1. In an aeroplane, a frame, main sustaining planes, auxiliarysustaining planes, ailerons, a frame for carrying said ailerons, meansfor simultaneously warping the ends of said planes and inclining saidaileron frame on an axis arranged longitudinally of said aeroplane, anelevating plane, and means for simultaneously actuating said eleratingplane and rotating said aileron frame on an axis arranged transverselyof said aeroplane.

2. In an aeroplane, a frame, sustaining planes, ailerons arrangedforwardly thereof, elevating planes arranged rearwardly there of, meansfor simultaneously warping the ends of said sustaining planes and movingsaid ailerons about a longitudinal'axis, means for rotating saidailerons on a transverse axis, and means for inclining said elevatingplanes.

3. In an aeroplane, a frame, sustaining planes, ailerons arrangedforwardly thereof, a frame for said ailerons, elevating planes at therear of said sustaining planes, means for warping said sustainingplanes, means for moving said aileron frame about a longitudinal axis,means for rotating .said ailerons on a transverse axis, and means forinclining said elevating planes. i

4. In an aeroplane, a frame, sustaining planes, elevating planes, meansfor actuating the same, a rudder, means for actuating the same, aileronsarranged forwardly of said sustaining planes, a frame therefor pivotedto said aeroplane frame, means for tilting said aileron frame on alongitudinal axis, means for. rotating said aileron frame on atransverse axis, and means for warping said sustalning planes.

5. In an aeroplane, a frame, sustaining planes, a rudder, an elevatingplane, a lever pivoted to said frame and directed forward, asupplemental frame in pivotal connection with said lever and adapted tomove into and out of the lateral, horizontal plane of the aeroplane,ailerons carried by said supplemental frame, and means for moving saidlever to move said ailerons into and out of the longitudinal,horizontal, plane .of said aeroplane. I

6. In an aeroplane, a vertical support, elevating planes, a leverpivoted to said support and normally held in'liorizontal osition, saidlever being provided with a Journal, a frame rotatable on said journalarranged transversely of said aeroplane, and ailerons on opposite endsof said rotatable frame, said aileron frame being rotatable on alongitudinal axis of said aeroplane when moved on said journal, andabout a transverse axis of said aeroplane When said lever is moved, andmeans for connecting said elevating planes with said aileron frame toactuate both simultaneously.

In testimony whereof I have signed my name to this specification in thepresence of two subscribing witnesses.

JOHN B. GROSS.

Witnesses:

ALEXANDER C. Hn'r'ron, DANIEL A. SULLIVAN.

